US20150292357A1 - Aircraft gas turbine having a core engine casing with cooling-air tubes - Google Patents
Aircraft gas turbine having a core engine casing with cooling-air tubes Download PDFInfo
- Publication number
- US20150292357A1 US20150292357A1 US14/559,527 US201414559527A US2015292357A1 US 20150292357 A1 US20150292357 A1 US 20150292357A1 US 201414559527 A US201414559527 A US 201414559527A US 2015292357 A1 US2015292357 A1 US 2015292357A1
- Authority
- US
- United States
- Prior art keywords
- core engine
- cooling
- engine casing
- air tubes
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/50—Building or constructing in particular ways
- F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This invention relates to an aircraft gas turbine having a core engine casing with cooling-air tubes in accordance with the generic part of claim 1 .
- the invention relates to an aircraft gas turbine having a core engine casing for a core engine, said core engine casing being provided on its outside with cooling-air tubes in order to supply cooling air from the compressor to a combustion chamber area and/ or to a turbine area.
- Modern turbofan gas turbines increasingly use smaller core engines which are operated at high or very high temperatures. This results in a smaller installation space radially outside the core engine casing for installing parts and components. This also applies to the supply of cooling air from the compressor area to the combustion chamber area or turbine area respectively, since the space available between the core engine casing and an inner wall of a bypass duct is very narrow.
- the object underlying the present invention is to provide a core engine casing of an aircraft gas turbine, which, while being simply designed and easily and cost-effectively producible, avoids the disadvantages of the state of the art and ensures both, an optimized cooling air routing and optimized thermal operating conditions.
- cooling-air tubes which extend substantially in the axial direction relative to the engine axis are provided on the outer wall of the core engine casing and in one piece with said outer wall.
- the one-piece embodiment with the core engine casing means that very little installation space is needed, since the walls of the cooling-air tubes, which can have a circular or other cross-section as required, also act as the wall of the core engine casing. This results in a very compact design.
- the distances prevailing in the state of the art between the outer wall of the core engine casing and separate tubes are thus avoided. This also makes it easier to attach further components to the core engine casing, as the installation space thus available is not limited by tubing, In the state of the art, a minimum distance is always needed between the tubes and other structural elements. Alternatively, it is possible to further reduce the space between the outer wall of the core engine casing and the inner wall of the bypass duct. Furthermore, it is not necessary in accordance with the invention, to provide curvatures in tubes to allow for thermal expansions and contractions.
- cooling-air tubes Due to direct mounting and integration of the cooling-air tubes into the outer wall of the core engine casing, cooling of the core engine casing by the cooling air conveyed by the cooling-air tubes is achieved at the same time.
- the cooling-air tubes connected in one piece to the outer wall also result in additional stability and strength of the core engine casing, so that its wall can be designed with a thinner cross-section.
- vibrations are suppressed and there are also smaller thermal tip clearance fluctuations relative to blades arranged inside the core engine casing, for example in the turbine area.
- the core engine casing is usually made by metal-cutting production methods, it is possible in a particularly simple way to design the cooling-air tubes, in respect of their outer contour, in one piece with the core engine casing.
- the cooling-air tubes can then be drilled or milled to provide them with the internal diameter required. If necessary, separate connecting fittings can be dispensed with, since openings can be provided directly into the cooling-air tubes from the inside of the outer wall of the core engine casing. Front-side openings of the cooling-air tubes can be closed by means of sealing plugs or similar,
- the core engine casing is divided into individual areas, in particular the compressor area, combustion chamber area and turbine area, which are made separately and then put together. It is favourable here when the cooling-air tubes too are connected at the ends during assembly, This can if necessary be achieved with the insertion of seals or similar between them.
- cooling-air tubes can here extend through the flanges, so that the latter can also be tightly connected to one another in a correspondingly simple way, as this is achieved by sealing off the casing areas from one another.
- cooling-air tubes together with the respective areas of the core engine casing
- cooling-air tubes are preferably spread aver the circumference, so that optimum conditions are achieved with regard to the cooling of the entire core engine casing and to the increase in the mechanical strength.
- the cooling-air tubes provided in accordance with the invention can also extend over differing axial part-areas of the core engine casing, for example from the compressor area to the combustion chamber area or from the compressor area to the turbine area.
- FIG. 1 shows a schematic representation of a gas-turbine engine in accordance with the present invention
- FIG. 2 shows a perspective outside view of a core engine casing in accordance with the present invention
- FIGS. 3-5 show perspective partial views of he core engine casing illustrated in FIG. 2 .
- the gas-turbine engine 10 in accordance with FIG. 1 is a generally represented example of a turbomachine where the invention can be used.
- the engine 10 is of conventional design and includes in the flow direction, one behind the other, an air inlet 11 , a fan 12 rotating inside a casing, an intermediate-pressure compressor 13 , a high-pressure compressor 14 , a combustion chamber 15 .
- the intermediate-pressure compressor 13 and the high-pressure compressor 14 each include several stages, of which each has an arrangement extending in the circumferential direction of fixed and stationary guide vanes 20 , generally referred to as stator vanes and projecting radially inwards from the core engine casing 21 in an annular flow duct through the compressors 13 , 14 .
- the compressors furthermore have an arrangement of compressor rotor blades 22 which project radially outwards from a rotatable drum or disk 26 linked to hubs 27 of the high-pressure turbine 16 or the intermediate-pressure turbine 17 , respectively.
- the turbine sections 16 , 17 , 18 have similar stages, including an arrangement of fixed stator vanes 23 projecting radially inwards from the casing 21 into the annular flow duct through the turbines 16 , 17 , 18 , and a subsequent arrangement of turbine rotor blades 24 projecting outwards from a rotatable hub 27 .
- the compressor drum or compressor disk 26 and the blades 22 arranged thereon, as well as the turbine rotor hub 27 and the turbine rotor blades 24 arranged thereon rotate about the engine axis 1 during operation.
- FIG. 2 shows a perspective representation of an exemplary embodiment of a core engine casing 21 , which includes, in a simplified view, a compressor area 29 , a combustion chamber area 30 and a turbine area 31 .
- the individual areas 29 , 30 and 31 are each connected by means of flanges 34 . This is shown in detail in enlarged representation in FIGS. 3 to 5 .
- FIGS. 3 and 5 it is shown that an outer wall 32 of the areas 29 , 30 , 31 of the core engine casing 21 is connected in one piece to cooling-air tubes 33 .
- the cooling-air tubes 33 are thus integrated into the outer wall 32 and are in close contact with said outer wall 32 .
- suitable openings are provided for passing the cooling-air tubes 33 through said flanges 34 .
- the outer wall 32 can be provided with a recess 35 for connecting the inner volume of the cooling-air tubes 33 to a suitable fitting or similar. Any free end areas of the cooling-air tubes 33 that occur can be closed by means of sealing elements 36 (see FIG. 4 ), not shown in detail. Angled cooling-air tubes 33 can be made by drilling from both sides (front and rear).
- the figures furthermore show marginal webs 37 , which can result from the one-piece production of the cooling-air tubes 33 and which serve to increase mechanical strength.
- the cooling-air tubes 33 can, as mentioned, be drilled or milled after the outer contour of the core engine casing 21 has been produced, for example using metal-cutting production methods.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- This invention relates to an aircraft gas turbine having a core engine casing with cooling-air tubes in accordance with the generic part of claim 1.
- In particular, the invention relates to an aircraft gas turbine having a core engine casing for a core engine, said core engine casing being provided on its outside with cooling-air tubes in order to supply cooling air from the compressor to a combustion chamber area and/ or to a turbine area.
- Modern turbofan gas turbines increasingly use smaller core engines which are operated at high or very high temperatures. This results in a smaller installation space radially outside the core engine casing for installing parts and components. This also applies to the supply of cooling air from the compressor area to the combustion chamber area or turbine area respectively, since the space available between the core engine casing and an inner wall of a bypass duct is very narrow.
- The measures known from the state of the art, i.e. installing separate tubes in a classic arrangement, can therefore be ruled out. Examples for separate tube connections of this type are shown in U.S. 2005/0252194 A1, U.S. Pat. No. 3,641,766 or GB 2 377 973 A. Due to the small installation space, it is not possible either to provide annular ducts for the cooling air, as already known from U.S. 2011/0247344 A1 or U.S. Pat. No. 6,227,800 B1. Annular ducts in, such a small installation space are very loss-prone and not efficient, since the boundary conditions for the airflow radially outside and radially inside are unfavourable due to their proximity.
- With the solutions known from the state of the art, in particular for the installation of separate tube systems, there is the further disadvantage that a large number of complex components is needed, which require a high production and assembly effort and are unfavourable in terms of thermal loading, in particular of the core engine casing. In addition, separate tube systems require additional measures (curvatures of tubes) to allow for thermal expansions or contractions.
- The object underlying the present invention is to provide a core engine casing of an aircraft gas turbine, which, while being simply designed and easily and cost-effectively producible, avoids the disadvantages of the state of the art and ensures both, an optimized cooling air routing and optimized thermal operating conditions.
- It is a particular object of the present invention to provide solution to the above problematics by the combination of the features of claim 1. Further advantageous embodiments of the present invention become apparent from the sub-claims.
- In detail, it is thus provided in accordance with the invention that cooling-air tubes which extend substantially in the axial direction relative to the engine axis are provided on the outer wall of the core engine casing and in one piece with said outer wall.
- The one-piece embodiment with the core engine casing means that very little installation space is needed, since the walls of the cooling-air tubes, which can have a circular or other cross-section as required, also act as the wall of the core engine casing. This results in a very compact design. The distances prevailing in the state of the art between the outer wall of the core engine casing and separate tubes are thus avoided. This also makes it easier to attach further components to the core engine casing, as the installation space thus available is not limited by tubing, In the state of the art, a minimum distance is always needed between the tubes and other structural elements. Alternatively, it is possible to further reduce the space between the outer wall of the core engine casing and the inner wall of the bypass duct. Furthermore, it is not necessary in accordance with the invention, to provide curvatures in tubes to allow for thermal expansions and contractions.
- Due to direct mounting and integration of the cooling-air tubes into the outer wall of the core engine casing, cooling of the core engine casing by the cooling air conveyed by the cooling-air tubes is achieved at the same time.
- The cooling-air tubes connected in one piece to the outer wall also result in additional stability and strength of the core engine casing, so that its wall can be designed with a thinner cross-section. In addition, vibrations are suppressed and there are also smaller thermal tip clearance fluctuations relative to blades arranged inside the core engine casing, for example in the turbine area.
- Since the core engine casing is usually made by metal-cutting production methods, it is possible in a particularly simple way to design the cooling-air tubes, in respect of their outer contour, in one piece with the core engine casing. The cooling-air tubes can then be drilled or milled to provide them with the internal diameter required. If necessary, separate connecting fittings can be dispensed with, since openings can be provided directly into the cooling-air tubes from the inside of the outer wall of the core engine casing. Front-side openings of the cooling-air tubes can be closed by means of sealing plugs or similar,
- In a particularly favourable embodiment of the invention, it is provided that the core engine casing is divided into individual areas, in particular the compressor area, combustion chamber area and turbine area, which are made separately and then put together. It is favourable here when the cooling-air tubes too are connected at the ends during assembly, This can if necessary be achieved with the insertion of seals or similar between them.
- It is particularly favourable when the individual areas of the core engine casing are connected to one another by means of flanges. The cooling-air tubes can here extend through the flanges, so that the latter can also be tightly connected to one another in a correspondingly simple way, as this is achieved by sealing off the casing areas from one another.
- Alternatively to production of the cooling-air tubes together with the respective areas of the core engine casing, it is also possible to produce the cooling-air tubes separately and then connect them by means of a suitable joining method, for example by welding, to the outer wall of the core engine casing.
- Several cooling-air tubes are preferably spread aver the circumference, so that optimum conditions are achieved with regard to the cooling of the entire core engine casing and to the increase in the mechanical strength.
- The cooling-air tubes provided in accordance with the invention can also extend over differing axial part-areas of the core engine casing, for example from the compressor area to the combustion chamber area or from the compressor area to the turbine area.
- The present invention is described in the following in light of the accompanying drawing, showing an exemplary embodiment. In the drawing,
-
FIG. 1 shows a schematic representation of a gas-turbine engine in accordance with the present invention, -
FIG. 2 shows a perspective outside view of a core engine casing in accordance with the present invention, -
FIGS. 3-5 show perspective partial views of he core engine casing illustrated inFIG. 2 . - The gas-
turbine engine 10 in accordance withFIG. 1 is a generally represented example of a turbomachine where the invention can be used. Theengine 10 is of conventional design and includes in the flow direction, one behind the other, anair inlet 11, afan 12 rotating inside a casing, an intermediate-pressure compressor 13, a high-pressure compressor 14, acombustion chamber 15. a high-pressure turbine 16, an intermediate-pressure turbine 7 and a low-pressure turbine 18 as well as anexhaust nozzle 19, all of which being arranged about a center engine axis 1. - The intermediate-
pressure compressor 13 and the high-pressure compressor 14 each include several stages, of which each has an arrangement extending in the circumferential direction of fixed andstationary guide vanes 20, generally referred to as stator vanes and projecting radially inwards from thecore engine casing 21 in an annular flow duct through thecompressors compressor rotor blades 22 which project radially outwards from a rotatable drum ordisk 26 linked tohubs 27 of the high-pressure turbine 16 or the intermediate-pressure turbine 17, respectively. - The
turbine sections casing 21 into the annular flow duct through theturbines turbine rotor blades 24 projecting outwards from arotatable hub 27. The compressor drum orcompressor disk 26 and theblades 22 arranged thereon, as well as theturbine rotor hub 27 and theturbine rotor blades 24 arranged thereon rotate about the engine axis 1 during operation. -
FIG. 2 shows a perspective representation of an exemplary embodiment of acore engine casing 21, which includes, in a simplified view, acompressor area 29, acombustion chamber area 30 and aturbine area 31. Theindividual areas flanges 34. This is shown in detail in enlarged representation inFIGS. 3 to 5 . - In
FIGS. 3 and 5 in particular, it is shown that anouter wall 32 of theareas core engine casing 21 is connected in one piece to cooling-air tubes 33. The cooling-air tubes 33 are thus integrated into theouter wall 32 and are in close contact with saidouter wall 32. In the area of theflanges 34, suitable openings are provided for passing the cooling-air tubes 33 through saidflanges 34. - As can be seen for example from
FIG. 3 , theouter wall 32 can be provided with arecess 35 for connecting the inner volume of the cooling-air tubes 33 to a suitable fitting or similar. Any free end areas of the cooling-air tubes 33 that occur can be closed by means of sealing elements 36 (seeFIG. 4 ), not shown in detail. Angled cooling-air tubes 33 can be made by drilling from both sides (front and rear). - The figures furthermore show
marginal webs 37, which can result from the one-piece production of the cooling-air tubes 33 and which serve to increase mechanical strength. The cooling-air tubes 33 can, as mentioned, be drilled or milled after the outer contour of thecore engine casing 21 has been produced, for example using metal-cutting production methods. - 1 Engine Axis
- 10 Gas-turbine engine/core engine
- 11 Air inlet
- 12 Fan
- 13 Intermediate-pressure compressor (compressor)
- 14 High-pressure compressor
- 15 Combustion chamber
- 16 High-pressure turbine
- 17 Intermediate-pressure turbine
- 18 Low-pressure turbine
- 19 Exhaust nozzle
- 20 Guide vanes
- 21 Core engine casing
- 22 Compressor rotor blades
- 23 Stator vanes
- 24 Turbine rotor blades
- 25 —
- 26 Compressor drum or disk
- 27 Turbine rotor hub
- 28 Exhaust cone
- 29 Compressor area
- 30 Combustion chamber area
- 31 Turbine area
- 32 Outer wall
- 33 Cooling-air tube
- 34 Range
- 35 Recess
- 36 Sealing element
- 37 Marginal web
Claims (8)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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DE102013224982.9A DE102013224982A1 (en) | 2013-12-05 | 2013-12-05 | Aircraft gas turbine with a core engine housing with cooling air tubes |
DE102013224982.9 | 2013-12-05 | ||
DE102013224982 | 2013-12-05 |
Publications (2)
Publication Number | Publication Date |
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US20150292357A1 true US20150292357A1 (en) | 2015-10-15 |
US9657593B2 US9657593B2 (en) | 2017-05-23 |
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ID=51999264
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US14/559,527 Expired - Fee Related US9657593B2 (en) | 2013-12-05 | 2014-12-03 | Aircraft gas turbine having a core engine casing with cooling-air tubes |
Country Status (3)
Country | Link |
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US (1) | US9657593B2 (en) |
EP (1) | EP2881552B1 (en) |
DE (1) | DE102013224982A1 (en) |
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US20170254216A1 (en) * | 2016-03-02 | 2017-09-07 | General Electric Company | Method and system for piping failure detection |
US10578028B2 (en) | 2015-08-18 | 2020-03-03 | General Electric Company | Compressor bleed auxiliary turbine |
US10711702B2 (en) | 2015-08-18 | 2020-07-14 | General Electric Company | Mixed flow turbocore |
CN114278402A (en) * | 2018-01-17 | 2022-04-05 | 通用电气公司 | Heat engine with cooled cooling air heat exchanger system |
CN114423930A (en) * | 2019-08-09 | 2022-04-29 | 赛峰飞机发动机公司 | Assembly of a manifold housing for a cooling device holding a turbine casing of a turbomachine |
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DE102016204660A1 (en) * | 2016-03-22 | 2017-09-28 | MTU Aero Engines AG | Method for producing a housing of a turbomachine and housing of a turbomachine |
WO2019161913A1 (en) * | 2018-02-23 | 2019-08-29 | Heico Befestigungstechnik Gmbh | Multiple screwdriver |
EP3755495B1 (en) | 2018-02-23 | 2021-08-11 | Heico Befestigungstechnik Gmbh | Multiple screwdriver |
EP3755496B1 (en) | 2018-02-23 | 2021-08-11 | Heico Befestigungstechnik Gmbh | Multiple screwdriver |
US11560843B2 (en) | 2020-02-25 | 2023-01-24 | General Electric Company | Frame for a heat engine |
US11326519B2 (en) | 2020-02-25 | 2022-05-10 | General Electric Company | Frame for a heat engine |
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US10578028B2 (en) | 2015-08-18 | 2020-03-03 | General Electric Company | Compressor bleed auxiliary turbine |
US10711702B2 (en) | 2015-08-18 | 2020-07-14 | General Electric Company | Mixed flow turbocore |
US20170254216A1 (en) * | 2016-03-02 | 2017-09-07 | General Electric Company | Method and system for piping failure detection |
US10196928B2 (en) * | 2016-03-02 | 2019-02-05 | General Electric Company | Method and system for piping failure detection in a gas turbine bleeding air system |
CN114278402A (en) * | 2018-01-17 | 2022-04-05 | 通用电气公司 | Heat engine with cooled cooling air heat exchanger system |
CN114423930A (en) * | 2019-08-09 | 2022-04-29 | 赛峰飞机发动机公司 | Assembly of a manifold housing for a cooling device holding a turbine casing of a turbomachine |
Also Published As
Publication number | Publication date |
---|---|
EP2881552A1 (en) | 2015-06-10 |
DE102013224982A1 (en) | 2015-06-11 |
US9657593B2 (en) | 2017-05-23 |
EP2881552B1 (en) | 2017-05-03 |
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